The energy required to move a satellite of mass m from an orbit of radius 2R to 3R around earth of mass M is

\frac{G M m}{12 R}

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\frac{G M m}{6 R}

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\frac{G M m}{8 R}

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\frac{G M m}{2 R}

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\frac{G M m}{3 R}

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Solution

The correct option is B $\frac{G M m}{6 R}$
$Δ W = Δ U$
$= m Δ V$
$= m (V_{f} - V_{i})$
$= m [(\frac{- G M}{3 R}) - (\frac{- G M}{2 R})]$
$= m . \frac{G M}{R} (\frac{1}{2} - \frac{1}{3}) = \frac{G m M}{6 R}$

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Energy required to move a body of mass m from an orbit of radius 2R to 3R is

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